阅读说明：本技术 一种挂箭式可回收低成本低轨道运载火箭 (Rocket-mounted recyclable low-cost low-orbit carrier rocket ) 是由 隋国发 于 2021-08-17 设计创作，主要内容包括：本发明公开了一种挂箭式可回收低成本低轨道运载火箭,包括芯级箭体、挂箭和火箭套罩,芯级箭体上设置挂箭,火箭套罩包括筒罩、端罩壳段和端罩,筒罩设置于芯级箭体的前端,筒罩内用于放置带有卫星载荷的二级箭体或亚轨道载荷,筒罩的底部设置用于安装二级箭体或亚轨道载荷的适配支座,筒罩的内壁上设置滑轨组合,适配支座上设置用于锁定二级箭体或亚轨道载荷的电控锁紧装置,滑轨组合与二级箭体或亚轨道载荷滑动配合连接；端罩壳段设置于筒罩的前端,端罩设置于端罩壳段的前端,端罩由与端罩壳段铰接的多瓣组成,多瓣端罩合拢后为半球状；本发明中的挂箭式可回收低成本低轨道运载火箭,能够100％整体回收,检测评定后可重复使用,复用价值更高。(The invention discloses a rocket-mounted recoverable low-cost low-orbit carrier rocket, which comprises a core-level rocket body, a rocket mount and a rocket cover, wherein the core-level rocket body is provided with the rocket mount, the rocket cover comprises a barrel cover, an end cover shell section and an end cover, the barrel cover is arranged at the front end of the core-level rocket body, the barrel cover is internally used for placing a second-level rocket body or sub-orbit load with satellite load, the bottom of the barrel cover is provided with an adaptive support used for mounting the second-level rocket body or sub-orbit load, the inner wall of the barrel cover is provided with a slide rail assembly, the adaptive support is provided with an electric control locking device used for locking the second-level rocket body or sub-orbit load, and the slide rail assembly is connected with the second-level rocket body or sub-orbit load in a sliding fit manner; the end cover shell section is arranged at the front end of the cylinder cover, the end cover is arranged at the front end of the end cover shell section and consists of a plurality of pieces hinged with the end cover shell section, and the end cover with a plurality of pieces is hemispherical after being folded; the rocket-mounted recoverable low-cost low-orbit carrier rocket can be recovered by 100% integrally, can be reused after detection and evaluation, and has higher reuse value.)

1. The utility model provides a recoverable low-cost low orbit carrier rocket of arrow-hanging which characterized in that: the rocket comprises a core-level rocket body, a rocket hanger and a rocket jacket cover, wherein the rocket hanger is arranged on the periphery of the core-level rocket body, the rocket jacket cover comprises a barrel cover, an end cover shell section and an end cover, the barrel cover is arranged at the front end of the core-level rocket body, a second-level rocket body with a satellite load or a sub-track load is placed in the barrel cover, an adaptive support used for mounting the second-level rocket body or the sub-track load is arranged at the bottom of the barrel cover, a sliding rail combination is arranged on the inner wall of the barrel cover, an electric control locking device used for locking the second-level rocket body or the sub-track load is arranged on the adaptive support, and the sliding rail combination is connected with the second-level rocket body or the sub-track load in a sliding fit manner; the end cover shell section is arranged at the front end of the cylinder cover, the end cover is arranged at the front end of the end cover shell section, the end cover is composed of a plurality of petals hinged with the end cover shell section, the end cover is hemispherical after being folded, the inner side of each petal end cover is connected with the end cover shell section through an end cover actuator, and the opening and closing of the end cover are controlled through the end cover actuator; the front end of the inner wall of the end shield shell section is also provided with a reverse thrust rocket, and the thrust direction of the reverse thrust rocket is opposite to the power direction of the core-stage rocket body.

2. The rocket-type recoverable low-cost low-orbit launch vehicle of claim 1, wherein: the front end of the second-level arrow body is provided with a satellite adapting bracket, and a satellite load is installed on the satellite adapting bracket.

3. The rocket-type recoverable low-cost low-orbit launch vehicle of claim 1, wherein: 4 or 8 hanging arrows are arranged, and every two hanging arrows are vertically connected in series and then uniformly distributed on the periphery of the core-level arrow body; the storage boxes of the two serially connected hanging arrows are connected by a box interval; the arrow hanging device comprises an arrow hanging power, a pressurization conveying system, an arrow hanging R box and an arrow hanging Y box.

4. The rocket-type recoverable low-cost low-orbit launch vehicle of claim 1, wherein: the core-level arrow body comprises a first-level power, a conveying pressurization system, a first-level power cabin, an engine cover, a first-level Y box, a first-level R box and a recovery landing support.

5. The rocket-type recoverable low-cost low-orbit launch vehicle of claim 1, wherein: the second grade arrow body includes second grade power, carries turbocharging system, second grade Y case, second grade R case and satellite adaptation support, satellite adaptation support set up in the front end of second grade R case.

6. The rocket-mounted recoverable low-cost low-orbit launch vehicle according to any of claims 3 to 5, wherein: the conveying pressurization system comprises a conveying pipeline, a pressurization pipeline, a valve gas cylinder and a fuel converter; the pressurization adopts two modes of autogenous pressurization or air source pressurization; the autogenous pressurization adopts the combination of gas storage of a high-pressure gas cylinder, opening adjustment of an electromagnetic valve to control gas flow and pore plate control gas flow to control pressure; adopting a 35MPa composite material gas cylinder; the core-level arrow body and each box body of the hanging arrow are respectively provided with a filling valve for filling propellant, a pressure sensor for measuring and an overflow valve for releasing pressure to ensure the working pressure of the box bodies; the fuel converter is characterized in that a medium of a front box for hanging the rocket is firstly conveyed to a core-level rocket body rear box through a fuel conveying pipe and is conveyed to an engine through the rear box.

7. The rocket-type recoverable low-cost low-orbit launch vehicle of claim 1, wherein: the sub-track load comprises air test equipment, air travel cabins and the like or cargo transport cabins.

8. The rocket-type recoverable low-cost low-orbit launch vehicle of claim 1, wherein: the cylinder cover is made of aluminum alloy skin or carbon fiber composite materials or glass fiber reinforced plastics.

9. The rocket-type recoverable low-cost low-orbit launch vehicle of claim 1, wherein: the slide rail combination is composed of a plurality of titanium alloy slide rails or aluminum alloy slide rails which are distributed in the circumferential direction.

10. The rocket-type recoverable low-cost low-orbit launch vehicle of claim 1, wherein: the end shield consists of 6-8 petals; the end cover is provided with a turnover grid wing.

Technical Field

The invention relates to the technical field of space rockets, in particular to a rocket-mounted recyclable low-cost low-orbit carrier rocket.

Background

With the continuous development of the aerospace field at home and abroad, how to reduce the cost of aerospace launch is one of the main challenges facing the whole aerospace industry, and the development of commercial aerospace puts higher requirements on low-cost launch and low-cost rockets! Especially for some low-altitude high-speed flight test launching, the recovery and the reuse of the carrier and the payload thereof are important measures for reducing the cost. In the beginning of the last century, research and tests on reusable aerospace transportation systems have been continuously carried out in the world by the aerospace major countries. From the technical characteristics of configuration, the reusable carrier can be divided into two categories, namely a horizontal recycling reusable carrier and a vertical recycling reusable carrier rocket. The premise of developing the research of vertical recovery and reuse of the carrier rocket is to develop the research of the carrier rocket sublevel recovery technology, for example, the falcon-9R rocket of the SpaceX company adopts a vertical return mode; the 'begal' booster proposed in russia also adopts a winged fly-back type. The space shuttle adopts a horizontal recovery mode of horizontal sliding recovery. The falcon rocket fairing of SpaceX company adopts parachute marine recovery in a split mode, and is a new application after the parachute of a satellite and an airship is recovered.

The prior art has the following defects:

at present, falcon-9R of SpaceX company and blue originated rockets realize first-stage rocket recovery; the falcon-9R fairing is separated into two sections for recovery after being thrown, and the falcon is mainly recovered at sea by adopting a parachute; the rockets above the second stage do not achieve recovery.

The domestic carrier rocket is not recycled, and the launching cost of the rocket is higher than that of the SpaceX company.

In summary, providing a rocket-mounted recoverable low-cost low-orbit launch vehicle is an urgent problem to be solved by those skilled in the art.

Disclosure of Invention

The invention aims to provide a rocket-mounted recoverable low-cost low-orbit carrier rocket, which solves the problems in the prior art, can be recovered by 100 percent integrally, can be reused after detection and evaluation, and has higher reuse value.

In order to achieve the purpose, the invention provides the following scheme:

the invention provides a rocket-mounted recoverable low-cost low-orbit carrier rocket, which comprises a core-level rocket body, a rocket mount and a rocket cover, wherein the rocket mount is arranged at the periphery of the core-level rocket body, the rocket cover comprises a barrel cover, an end cover shell section and an end cover, the barrel cover is arranged at the front end of the core-level rocket body, a secondary rocket body or sub-orbit load with a satellite load is placed in the barrel cover, an adaptive support used for mounting the secondary rocket body or the sub-orbit load is arranged at the bottom of the barrel cover, a slide rail combination is arranged on the inner wall of the barrel cover, an electric control locking device used for locking the secondary rocket body or the sub-orbit load is arranged on the adaptive support, and the slide rail combination is connected with the secondary rocket body or the sub-orbit load in a sliding fit manner; the end cover shell section is arranged at the front end of the cylinder cover, the end cover is arranged at the front end of the end cover shell section, the end cover is composed of a plurality of petals hinged with the end cover shell section, the end cover is hemispherical after being folded, the inner side of each petal end cover is connected with the end cover shell section through an end cover actuator, and the opening and closing of the end cover are controlled through the end cover actuator; the front end of the inner wall of the end shield shell section is also provided with a reverse thrust rocket, and the thrust direction of the reverse thrust rocket is opposite to the power direction of the core-stage rocket body.

Preferably, a satellite adapting bracket is arranged at the front end of the second-stage arrow body, and a satellite load is installed on the satellite adapting bracket.

Preferably, the number of the hanging arrows is 4 or 8, and every two hanging arrows are vertically connected in series and then uniformly distributed on the periphery of the core-level arrow body; the storage boxes of the two serially connected hanging arrows are connected by a box interval; the arrow hanging device comprises an arrow hanging power, a pressurization conveying system, an arrow hanging R box and an arrow hanging Y box.

Preferably, the core-level arrow body comprises a primary power, a conveying pressurization system, a primary power cabin, an engine cover, a primary Y box, a primary R box and a recovery landing support.

Preferably, the second grade arrow body includes second grade power, carries turbocharging system, second grade Y case, second grade R case and satellite adaptation support, satellite adaptation support set up in the front end of second grade R case.

Preferably, the delivery pressurization system comprises a delivery pipeline, a pressurization pipeline, a valve gas cylinder and a fuel converter; the pressurization adopts two modes of autogenous pressurization or air source pressurization; the autogenous pressurization adopts the combination of gas storage of a high-pressure gas cylinder, opening adjustment of an electromagnetic valve to control gas flow and pore plate control gas flow to control pressure; adopting a 35MPa composite material gas cylinder; the core-level arrow body and each box body of the hanging arrow are respectively provided with a filling valve for filling propellant, a pressure sensor for measuring and an overflow valve for releasing pressure to ensure the working pressure of the box bodies; the fuel converter is characterized in that a medium of a front box for hanging the rocket is firstly conveyed to a core-level rocket body rear box through a fuel conveying pipe and is conveyed to an engine through the rear box.

Preferably, the sub-track load comprises air test equipment or air travel cabins or the like or cargo transport cabins.

Preferably, the cylinder cover is made of aluminum alloy skin or carbon fiber composite material or glass fiber reinforced plastic.

Preferably, the slide rail combination is composed of a plurality of titanium alloy slide rails or aluminum alloy slide rails which are circumferentially distributed.

Preferably, the end shield consists of 6-8 lobes; the end cover is provided with a turnover grid wing.

Compared with the prior art, the invention has the following beneficial technical effects:

1. the low-cost low-orbit carrier rocket can be recovered by 100 percent integrally, can be reused after detection and evaluation, and has higher reuse value.

2. The end shield shell section combination, the cylinder shield slide rail combination, the core-level arrow body and the hanging arrow are integrally recovered, so that the large amount of manpower and material resource consumption caused by tracking, monitoring and recovery of a recovery ship for fairing split marine recovery or parachute recovery is avoided.

3. By using the protection of the 'low orbit carrier rocket' rocket cover, the flying environment of the second-level rocket body structure in the process of flying the atmosphere is greatly improved, the design requirement of the second-level rocket body structure is reduced, and the development and production cost can be further reduced.

4. Effectively reducing the functional cost of the carrier rocket, and predicting that the launching cost of the low-orbit load can be reduced by 50 percent compared with that of a disposable rocket.

5. The reuse of the low-orbit carrier rocket can greatly shorten the development and launching period of the rocket. The launch cost of the launch vehicle is reduced, and a foundation is laid for intercontinental transportation, space travel, space tests, space industry and space economic development.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.

FIG. 1 is a schematic view of a rocket-type recoverable low-cost low-orbit launch vehicle according to an embodiment of the invention;

FIG. 2 is a schematic structural view of a core stage arrow body and a two-stage arrow body separated front end cover in an open state according to an embodiment of the present invention;

FIG. 3 is a schematic structural view of a core-level arrow, a second-level arrow separation, and a second-level arrow flight state according to an embodiment of the present invention;

FIG. 4 is a schematic structural view of a mid-stage split aft end cap-in-cap, low orbit launch vehicle in a return state in accordance with an embodiment of the present invention;

FIG. 5 is a schematic structural diagram illustrating a state in which the end cover can be adjusted to be opened according to a stable requirement when the rocket returns to the ground according to the first embodiment of the present invention;

FIG. 6 is a schematic structural view of a core-level arrow and its barrel casing in an overall landing return state according to an embodiment of the present invention;

FIG. 7 is a schematic structural view of a rocket-type recoverable low-cost low-orbit launch vehicle according to a second embodiment of the invention;

FIG. 8 is a schematic structural view of a second embodiment of the sub-rail load decoupling front end cover in an open position;

FIG. 9 is a schematic structural diagram illustrating a second embodiment of the present invention in a sub-orbital loading flight state;

FIG. 10 is a schematic view of the second embodiment of the present invention showing the configuration of the inter-stage separation rear end cap and the low orbit launch vehicle in a return state;

FIG. 11 is a schematic structural diagram illustrating a state in which the end cover can be adjusted to open according to a stable requirement when the rocket returns to the ground according to the second embodiment of the present invention;

FIG. 12 is a schematic structural view of a second embodiment of the present invention, showing the core-level arrow and its barrel casing in an overall landing return state;

in the figure: 1-core-level rocket body, 2-rocket sleeve cover, 3-rocket hanger, 4-barrel cover, 5-end cover shell section, 6-end cover, 7-adaptive support, 8-slide rail combination, 9-secondary rocket body, 10-sub-orbit load, 11-satellite adaptive support, 12-satellite load, 13-end cover actuator, 14-thrust rocket, 15-reversible grid wing and 16-fuel conveying pipe.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

The invention aims to provide a rocket-mounted recoverable low-cost low-orbit carrier rocket, which aims to solve the problems in the prior art.

In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.

The first embodiment is as follows:

the rocket-mounted recoverable low-cost low-orbit carrier rocket in the embodiment comprises a core-level rocket body 1, a rocket mount 3 and a rocket cover 2, wherein the rocket cover 2 comprises a barrel cover 4, an end cover shell section 5 and an end cover 6, the barrel cover 4 is arranged at the front end of the core-level rocket body 1, a second-level rocket body 9 is arranged in the barrel cover 4, an adaptive support 7 for mounting the second-level rocket body 9 is arranged at the bottom of the barrel cover 4, a sliding rail assembly 8 is arranged on the inner wall of the barrel cover 4, an electronic control locking device for locking the second-level rocket body 9 is arranged on the adaptive support 7, the sliding rail assembly 8 is connected with the second-level rocket body 9 in a sliding fit manner, a satellite adaptive support 11 is arranged at the front end of the second-level rocket body 9, and a satellite load 12 is mounted on the satellite adaptive support 11; the end shield shell section 5 is arranged at the front end of the cylinder shield 4, the end shield 6 is arranged at the front end of the end shield shell section 5, the end shield 6 consists of a plurality of petals hinged with the end shield shell section 5, the end shield 6 is hemispherical after being folded, the inner side of each petal end shield 6 is connected with the end shield shell section 5 through an end shield actuator 13, and the opening and closing of the end shield 6 are controlled through the end shield actuator 13; the front end of the inner wall of the end shield shell section 5 is also provided with a reverse thrust rocket 14, and the thrust direction of the reverse thrust rocket 14 is opposite to the power direction of the core-stage rocket body 1.

In the embodiment, 4 or 8 hanging arrows 3 are arranged, and every two hanging arrows 3 are vertically connected in series and then uniformly distributed on the periphery of the core-level arrow body 1; the storage tanks of the two serially connected hanging arrows 3 are connected by a tank interval section 17; the arrow hanging 3 comprises an arrow hanging power, a pressurization conveying system, an arrow hanging R box and an arrow hanging Y box.

In this embodiment, the core-level rocket body 1 includes a first-level power, a conveying system, a pressurizing system, a first-level power cabin, an engine hood, a first-level Y box, a first-level R box and a recovery landing support (the connection relation and the working principle of each part are conventional technical means of rockets, and no further description is given);

the power system of the core-level arrow body and the hanging arrow is specifically as follows: the core-level arrow body 1 is provided with 5X80t, the lower part of the arrow 3 is provided with a 4X80t liquid oxygen kerosene engine, and the takeoff thrust is as follows: 1040 t. Core level arrow body 1 engine layout: the middle engine swings bidirectionally and can adjust the thrust between 50 percent and 100 percent, and the four engines which are uniformly distributed at intervals of 90 degrees on the outer ring can swing to control the flight attitude in a single way. Hanging arrow 3 engine layout: four engines are uniformly distributed at intervals of 90 degrees in the annular direction, and swinging pipes are not needed. The engine adopts the open type pump backswing technology to realize the lowest cost of the attitude control and rocket recovery functions!

In this embodiment, the secondary arrow body 9 includes a secondary power and pressurizing conveying system, a secondary Y box, a secondary R box, and a satellite adapting bracket 11, and the satellite adapting bracket 11 is arranged at the front end of the secondary R box; the secondary power is a middle 80-ton liquid oxygen kerosene engine, and four 15-ton unidirectional swinging attitude control engines are uniformly distributed at 90 degrees on an outer ring.

Conveying pressurization system: mainly comprises a conveying pipeline, a pressurizing pipeline, a valve gas cylinder, a fuel converter and the like. The pressurization adopts two modes of self-generation pressurization and gas source pressurization; the autogenous pressurization adopts the combination of gas storage of a high-pressure gas cylinder, opening adjustment of an electromagnetic valve to control gas flow and pore plate control gas flow to control pressure; a35 MPa composite material gas cylinder is adopted. Filling valves are respectively arranged on the box bodies (the core-level arrow body, the front box (R, Y) and the rear box (R, Y) of the arrow hanging body) of the core-level arrow body 1 and the arrow hanging body 3 to fill propellant, the pressure sensors measure the propellant and the relief valves to ensure the working pressure of the box bodies. The fuel converter is characterized in that a medium in a front box of a hanging arrow 3 is firstly conveyed to a rear box of a core-level arrow body 1 through a fuel conveying pipe 16 and is conveyed to an engine through the rear box, long-distance medium conveying of the outer wall of the arrow body is eliminated, a POGO restraining system is eliminated, and therefore a pressure accumulator device and the like can be eliminated.

In the embodiment, when each petal of the end shield 6 is opened in place under the action of the actuator, the second-stage rocket body 9 is linked with the adaptive support 7 for unlocking, the reverse thrust rocket 14 is ignited, and the load slides out and separates along the sliding rail of the first-stage cylinder cover 4; the second-stage arrow body 9 and the load thereof continue to fly to perform a loading task. The end shield 6 is opened (without throwing and falling), the first stage and the second stage are separated and then closed, and the rocket sleeve shield 2, the core-stage rocket body 1 and the hanging rocket 3 form a 'low orbit carrier rocket' to be integrally recovered. The combination of the barrel cover slide rail and the end cover shell section can be designed into an integrated structure, the structure is divided into two parts, and the process operation such as process, production, test and the like is more convenient in main consideration.

In this embodiment, the barrel casing 4 is made of an aluminum alloy skin or a carbon fiber composite material or glass fiber reinforced plastic, the slide rail assembly 8 is composed of a plurality of circumferentially distributed titanium alloy slide rails or aluminum alloy slide rails, the surfaces of the slide rails are solid-lubricated, and the slide rails are limited and lubricated during load mounting and separation, so that loads are protected from being damaged by external force.

In this embodiment, the end shield 6 is composed of 6-8 flaps, and each flap of the end shield 6 is actuated to open or close by an end shield actuator 13; the end cover actuator 13 is an electric or hydraulic actuating mechanism or a steering engine, and gradually adjusts the opening of the fairing according to the required opening.

In the embodiment, the end shield 6 is provided with the turnable grid wings 15, the turnable grid wings 15 are attached to the outer side of the end shield 6 and can be connected in a welding mode, the end shield 6 is opened when the rocket is recovered and landed, and the end shield 6 and the grid wings thereof play a role in pneumatic rectification and stabilization. In the process that the sub-orbit carrier rocket returns to the ground, the end shield 6 can adjust the opening degree according to the stability requirement, gradually open or close the closing shield, replace the effect of the grid wing in the traditional rocket return process, and stabilize the posture of the rocket.

The structure and installation design of the secondary storage box (the synthesis of the secondary Y box and the secondary R box): the storage tank is made of 2214/2219 material; the bottom of the box adopts the toper bottom, improves the bottom of the box rigidity, reduces the shaping technology degree of difficulty. The storage tank shell section adopts a structure of skin, ring frame and row strip, the skin ensures sealing, and the ring frame and the row strip increase strength and rigidity; the storage tank welding adopts a stirring welding technology, and the strength coefficient of a welding seam is improved. The two front and rear storage tanks at the second stage are installed in a concave-convex embedding mode, so that the space is saved; the concave-convex embedding mode of the storage box is not a common-bottom structure, so that the vacuum technical requirement of the common-bottom structure is avoided, and the process difficulty and the production cost are reduced.

Modular design:

under the condition that the diameter of a 3.3 m-shaped core-level arrow body 1 is not changed, two or four hanging arrows can be hung according to the change requirement of the load weight of 10-50 t, the length of the arrow body can be adjusted between 50 m-80 m, and the thrust of a corresponding single engine of a power system can be adjusted and exchanged between 50 t-120 t.

The same 3.3m arrow body structure production line, the adaptation face is wider. Production lines with more specifications are not required to be built, so that the fixed asset investment of production lines with other specifications is saved, and the product cost is reduced.

The diameters of the hanging arrows 3 and the diameters of the core-level arrow bodies can be uniform or non-uniform; if the existing production lines with different specifications exist, the structure size can be optimized and adjusted at low cost according to the existing production capacity.

The 3.3m arrow diameter configuration can also be adjusted between 2m and 5m according to the load weight requirement and the cost optimization requirement.

In this embodiment, the flight procedure and principle of the rocket-type recoverable low-cost low-orbit launch vehicle are as follows:

1) each part of the rocket is installed and debugged, and each system and the overall test preparation before launching are completed; the launch preparation phase is the same as a traditional rocket, and the whole rocket is pushed to lift off by an engine relying on the core-level rocket body 1 and the rocket 3.

2) After the rocket passes through the atmosphere and reaches the designated separation height, the end shield 6 is opened outwards under the action of an end shield actuator 13, as shown in fig. 2; the end shield 6 is opened and the engine with the core-stage arrow body 1 and the hanging arrow 3 is closed.

3) The engine of the reverse thrust rocket 14 is started, the core-stage rocket body 1 is separated from the second-stage rocket body 9, as shown in fig. 3, the second-stage rocket body 9 continues to fly to a preset orbit, and the star rocket is separated.

4) The core-level rocket body 1 and the second-level rocket body 9 are separated, and the rear end cover 6 is closed, as shown in fig. 4, the low-orbit carrier rocket (the core-level rocket body 1, the rocket sleeve cover 2 and the rocket hooking body 3) slowly returns to the atmosphere under the action of the earth gravity or the first-level rocket engine and flies to the ground. The height is preset before landing, the posture of the rocket is continuously adjusted to slowly descend under the combined action of the thrust of the first-stage intermediate engine and the thrust of each engine, the recovery landing bracket is opened before the rocket lands on the ground, and finally the rocket lands on the specified recovery place, as shown in figure 6.

5) The end shield 6 is designed to be rectified stably, and replaces the effect of a grid wing in the traditional rocket return process, so that the posture of the rocket is stabilized. During the process of returning the low-orbit launch vehicle to the ground, the end shield 6 can be adjusted to open according to the stability requirement, and gradually opens or closes the closing shield, as shown in fig. 5.

6) The low-orbit carrier rocket is returned to the factory after being recovered, can be continuously used after being qualified for overhauling, and is used for a new sub-orbit launching task.

Example two:

as shown in fig. 7. The difference between this embodiment and the first embodiment is:

the cylinder cover 4 is internally used for placing a sub-rail load 10, the bottom of the cylinder cover 4 is provided with an adaptive support 7 for mounting the sub-rail load 10, the adaptive support 7 is provided with an electric control locking device for locking the sub-rail load 10, and the sliding rail combination 8 is connected with the sub-rail load 10 in a sliding fit manner; wherein the sub-track load 10 comprises an aerospace test rig or aerospace travel cabin or the like or a cargo transport cabin.

In this embodiment, the flight procedure and principle of the rocket-type recoverable low-cost low-orbit launch vehicle are as follows:

1) each part of the rocket is installed and debugged, and each system and the overall test preparation before launching are completed; the launching preparation stage is the same as that of the traditional rocket, and the whole rocket is pushed to lift off by an engine of a core-level rocket body 1 and a rocket hanging body 3;

2) after the rocket passes through the atmosphere and reaches the designated separation height, the end shield 6 is opened outwards under the action of the end shield actuator 13, as shown in fig. 8; end shield 6 is open and core stage arrow body 1 engine is off.

3) The engine of the thrust-reversing rocket 14 is started, the sub-orbital loads 10 are separated from the core-stage rocket body 1, and the sub-orbital loads 10 continue to fly to perform subsequent tasks as shown in fig. 9.

4) The sub-orbital load 10 separates the rear end cover 6 and closes, as shown in fig. 10, the sub-orbital launch vehicle (core-level rocket body 1+ rocket cover 2+ rocket mount 3) slowly returns to the atmosphere under the action of the earth gravity or the engine of the core-level rocket 1, and flies to the ground. The height is preset before landing, the posture of the rocket is continuously adjusted to slowly descend under the combined action of the thrust of the first-stage intermediate engine and the thrust of each engine, the recovery landing bracket is opened before the rocket lands on the ground, and finally the rocket lands on the specified recovery place, as shown in figure 12.

5) The end shield 6 is designed to be rectified stably, and replaces the effect of a grid wing in the traditional rocket return process, so that the posture of the rocket is stabilized. In the process of returning the sub-orbit launch vehicle to the ground, the end shield 6 can be adjusted to open according to the stability requirement, and gradually opens or closes the closing shield, as shown in fig. 11.

6) And returning the recovered suborbital carrier rocket to a factory for maintenance, and continuously using the carrier rocket after the maintenance is qualified for a new suborbital launching task.

The principle and the implementation mode of the invention are explained by applying specific examples, and the description of the above examples is only used for helping understanding the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In summary, this summary should not be construed to limit the present invention.